FLIGHT CONTROL SYSTEMS

• US 20070267548A1
• Filed: 01/31/2007
• Published: 11/22/2007
• Est. Priority Date: 05/17/2006
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Cessna Aircraft Company (Textron Inc)
• Inventors: Palmer, Mark, Ciholas, Philippe
• Granted Patent: US 8,401,716 B2
• Time in Patent Office: Days
• US Class Current: 244/223
• CPC Class Codes: B64C 13/38 with power amplification
• CPC Class Codes: B64C 13/507 with artificial feel
• CPC Class Codes: B64C 9/04 with compound dependent movements
• CPC Class Codes: B64C 9/10 one surface adjusted by movement of another, e.g. servo tabs B64C9/04 takes precedence; adjusting surfaces of different type or function B64C9/12

Abstract

A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces.

Claims

1. A flight control system for an aircraft, said system comprising:

a control surface having first and second portions;

an at least partially mechanically controlled actuator for controllably positioning said first portion; and

an electronically controlled actuator for controllably positioning said second portion.

2. The system of claim 1 wherein said at least partially mechanically controlled actuator is a mechanically driven power control unit (PCU).

3. The system of claim 1 wherein said at least partially mechanically controlled actuator is adapted to receive a mechanical input from a user and output an angular position of said first portion of said control surface corresponding to said mechanical input.

4. The system of claim 3 comprising:

a mechanical input of said at least partially mechanically controlled actuator,

said mechanical input receiving a translation from a pilot via a linkage.

5. The system of claim 4 wherein said at least partially mechanically controlled actuator is adapted to be unidirectional in that forces onto said first portion of said control surface are not allowed to influence said linkage.

6. The system of claim 4 wherein said linkage is coupled to an artificial feel system which gives the pilot feedback simulating the feel of an mechanically actuated system.

7. The system of claim 4 wherein said artificial feel system comprises a control stick having a springback mechanism which provides greater resistance the further said stick is moved away from neutral.

8. The system of claim 1 wherein the control surface is selected from the group comprising flaps, rudders, elevators, and ailerons.

9. A flight control system for an aircraft, said system comprising:

a control surface having first and second portions;

a substantially mechanical arrangement for controllably positioning said first portion; and

an electronically controlled actuator for controllably positioning said second portion.

10. The system of claim 9 wherein said substantially mechanical arrangement includes a mechanical linkage which receives mechanical input from a user in a cockpit of said aircraft.

11. The system of claim 10 wherein said linkage is translated using a mechanism in said cockpit.

12. The system of claim 11 wherein said mechanism is one of foot controlled and hand controlled and said mechanism includes an artificial feel system.

13. The system of claim 12 wherein said artificial feel system includes a springback device which is coupled to said mechanism for the purpose of simulating the feel of a purely mechanical system.

14. The system of claim 11 comprising:

at least one force sensor on said mechanism, said sensor being adapted to measure operator effort applied to said mechanism to create a signal;

a computing device adapted to receive said signal;

said computing device being adapted to control said electronically controlled actuator for the purpose of controllably positioning said second portion in response to said signal.

15. The system of claim 9 wherein said control surface is selected from the group comprising flaps, rudders, elevators, and ailerons.

16. The system of claim 15 wherein said control surface includes a third portion, said third portion being substantially electronically controlled in response to said signal.

17. A method of operating a control surface on an aircraft, said method comprising:

comprising said control surface of a first portion and a second portion;

providing a device which receives inputs from a user via a mechanical system and angularly displaces said first portion;

electronically controlling said second portion to angularly displace said second portion in a same angular direction as said first portion.

18. The method of claim 17 comprising:

using a sensor on said mechanical system and a computer to accomplish said electronically controlling step.

19. The method of claim 18 comprising:

locating said sensor on a control stick; and

measuring operator effort using said sensor.

20. The method of claim 18 comprising:

including an artificial feel system in said mechanical system, said artificial feel system including a spring back device which provides resistance the further said first portion is moved away from neutral.